CN110524186A - Engine in situ component is repaired - Google Patents
Engine in situ component is repaired Download PDFInfo
- Publication number
- CN110524186A CN110524186A CN201910436217.XA CN201910436217A CN110524186A CN 110524186 A CN110524186 A CN 110524186A CN 201910436217 A CN201910436217 A CN 201910436217A CN 110524186 A CN110524186 A CN 110524186A
- Authority
- CN
- China
- Prior art keywords
- abradable material
- gap
- airfoil
- measurement
- circumferential direction
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/005—Repairing methods or devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
- B05B13/00—Machines or plants for applying liquids or other fluent materials to surfaces of objects or other work by spraying, not covered by groups B05B1/00 - B05B11/00
- B05B13/02—Means for supporting work; Arrangement or mounting of spray heads; Adaptation or arrangement of means for feeding work
- B05B13/0278—Arrangement or mounting of spray heads
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
- B05B15/00—Details of spraying plant or spraying apparatus not otherwise provided for; Accessories
- B05B15/70—Arrangements for moving spray heads automatically to or from the working position
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
- B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
- B23P6/005—Repairing turbine components, e.g. moving or stationary blades, rotors using only replacement pieces of a particular form
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/16—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring distance of clearance between spaced objects
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/20—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring contours or curvatures, e.g. determining profile
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
- B29C73/02—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using liquid or paste-like material
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/80—Repairing, retrofitting or upgrading methods
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A method of for repairing turbogenerator, comprising: determine that the measurement in the gap between the outer end and tyre of multiple airfoils is greater than predetermined amount；And the measurement in the gap between outer end and tyre of the in-situ deposition abradable material to reduce multiple airfoils is taken outside.
Description
Technical field
This theme relates generally to a kind of system and method for the abradable material in repairing gas turbine engine.
Background technique
At least some of gas-turbine unit includes: compressor section with serial flow arrangement comprising for compressing stream
Cross the low pressure compressor and high pressure compressor of the air of engine；Burner is used to mix fuel with compressed air, so that
Mixture can be ignited；And turbine comprising for providing high-pressure turbine and the low pressure whirlpool of power to compressor section
Wheel.
Each of compressor and turbine may include Multi-stage rotary airfoil, for flowing through air therein addition energy
Amount therefrom extracts energy.One or more grades of airfoil can have the abradable layer around it, with its radially outer edge shape
At closer sealing, to improve the efficiency of turbogenerator.It should be understood, however, that by normal operating process, it can
Wearing course may be worn.For example, by cycle of engine, due to for example changing engine components caused by operation temperature
Expansion and contraction can be such that abradable layer and the radially outer tip of the grade of its rotating airfoils part surrounded more closely contacts.This
Outside, the metallic particles from engine can form abradable layer, so that abradable layer also becomes easier to expand and shrink.
Therefore, after a certain amount of abrasion, it is necessary to remove turbogenerator from the wing, dismantle with the abradable layer of exposure
And it places under repair.This is an expensive job in time.Therefore, the improvement system of the abradable layer in fixing over an engine and/
Or method will be useful.
Summary of the invention
Aspects and advantages of the present invention will illustrate partly in the following description, or can from description it is clear that
Or it can be learnt by practicing the present invention.
In one aspect of the present disclosure, a kind of method for repairing turbogenerator is provided, the turbogenerator packet
Airfoil rotation grade and the tyre around airfoil rotation grade are included, airfoil rotation grade includes the multiple airfoils for limiting outer end.
This method includes that the measurement in the gap between the outer end and tyre of determining multiple airfoils is greater than predetermined amount；And original is taken outside
The measurement in the gap between outer end and tyre of the position deposition abradable material to reduce multiple airfoils.
In certain illustrative aspects, taking in-situ deposition abradable material outside includes that use is attached in multiple airfoils
The jet module of at least one airfoil deposit abradable material.
For example, taking in-situ deposition abradable material outside further includes revolving multiple airfoils in certain illustrative aspects
Turn, while abradable material in-situ deposition being taken outside.
In certain illustrative aspects, turbogenerator limits radial direction and circumferential direction, and wherein determines multiple wings
The measurement in the gap between the outer end and tyre of type part includes determining the radially two dimension measurement with the gap of circumferential direction.
In certain illustrative aspects, turbogenerator limits axial direction, radial direction and circumferential direction, and wherein really
The measurement in the gap between the outer end and tyre of fixed multiple airfoils includes determining in axial direction, radial direction and circumferential direction
Gap three-dimensional measurement.
In certain illustrative aspects, turbogenerator limits circumferential direction, and wherein takes in-situ deposition outside and can grind
Consumption material is included in outer take and deposits abradable material in an uneven manner along circumferential direction.
For example, deposition abradable material includes edge in an uneven manner along the circumferential direction in certain illustrative aspects
Circumferential direction deposit abradable material in an uneven manner, so as to cause the uneven measurement in gap along circumferential direction.
In certain illustrative aspects, this method further includes at least part in situ for removing existing abradable material.
In certain illustrative aspects, this method further includes that reshaping in situ is deposited on the abradable material taken outside.
For example, reshaping in situ is deposited on the abradable material taken outside including the use of attached in certain illustrative aspects
The reshaping tool original position reshaping at least one airfoil being connected in multiple airfoils is deposited on the abradable material taken outside
Material.
For example, in certain illustrative aspects, reshaping in situ be deposited on the abradable material taken outside further include make it is multiple
Airfoil rotation, while reshaping in situ is deposited on the abradable material taken outside.
In certain illustrative aspects, multiple airfoils that airfoil rotates grade are multiple rotor blades.
In certain illustrative aspects, taking in-situ deposition abradable material outside includes that use extends through turbogenerator
Opening snakelike arm tool in-situ deposition abradable material.
In an exemplary embodiment of the disclosure, a kind of repair outfit is provided, for repairing the wing for surrounding turbogenerator
Type part rotates the abradable layer of the tyre of grade.The repair outfit includes sensing module, which includes sensor, the sensing
Device is configured to the data of the measurement in the gap between sensing the first airfoil of instruction and the abradable layer of tyre；With injection mould
Block, on the airfoil for being configured to be removably attached to airfoil rotation grade, which includes for by abradable material
Expect the nozzle being ejected on abradable layer.
In some of the exemplary embodiments, jet module is configured to be removably attached to the of airfoil rotation grade
Two airfoils, and wherein sensing module is configured to be removably attached to the first airfoil of airfoil rotation grade.
In some of the exemplary embodiments, repair outfit further includes forming module, which is configured to reshaping
The abradable material being ejected on abradable layer.
For example, in some of the exemplary embodiments, forming module is configured to be removably attached to airfoil rotation
The third airfoil of grade.
In some of the exemplary embodiments, repair outfit further includes controller, wherein sensing module and jet module
It is operably coupled to controller.
For example, in some of the exemplary embodiments, controller includes one or more processors and memory, wherein storing
Device storing data, the data include the instruction for making repair outfit execute function when executed by one or more processors, the function
It can include the two dimension measurement for determining the gap of the radial direction along turbogenerator and the circumferential direction along turbogenerator.
For example, in some of the exemplary embodiments, which further includes determining radially, along circumferential direction and along whirlpool
The three-dimensional measurement in the gap of the axial direction of turbine.
With reference to the following description and the appended claims, be better understood with these and other features of the invention, aspect and
Advantage.Comprising in the present specification and constituting part thereof of attached drawing and showing the embodiment of the present invention, and together with specification
Principle for explaining the present invention.
Detailed description of the invention
The complete and feasible disclosure of the invention for those of ordinary skill in the art is elaborated in the description, including
Its optimal mode refers to attached drawing, in which:
Fig. 1 is the schematic cross-sectional view according to the gas-turbine unit of the illustrative aspect of the disclosure.
Fig. 2 is the near-sighted viewgraph of cross-section of the rear end of the exemplary gas turbogenerator of Fig. 1.
Fig. 3 is the exemplary gas turbogenerator according to Fig. 1 including depositing system of the illustrative aspect of the disclosure
Rotating airfoils part grade near-sighted axial view.
Fig. 4 is the close-up view of the first airfoil of the grade of the rotating airfoils part of Fig. 3.
The grade and the gap between the abradable layer of the grade of the airfoil that Fig. 5 is the rotating airfoils part of depiction 3
The figure of first measurement.
The grade and the gap between the abradable layer of the grade of the airfoil that Fig. 6 is the rotating airfoils part of depiction 3
The figure of second measurement.
The grade and the gap between the abradable layer of the grade of the airfoil that Fig. 7 is the rotating airfoils part of depiction 3
The figure of third measurement.
Fig. 8 is the close-up view of the second airfoil of the grade of the rotating airfoils part of Fig. 3.
Fig. 9 is the close-up view of the third airfoil of the grade of the rotating airfoils part of Fig. 3.
Figure 10 is horizontal according to the myopia of the rear end of the exemplary gas turbogenerator of disclosure another exemplary embodiment
Sectional view.
Figure 11 is the flow chart according to the method for repairing gas turbine engine of the illustrative aspect of the disclosure.
Specific embodiment
Now with detailed reference to the embodiment of the present invention, one or more example is shown in the accompanying drawings.Detailed description makes
The feature in attached drawing is referred to number and alphabetic flag.Same or similar label in drawing and description has been used for referring to
The same or similar part of the invention.
As it is used herein, term " first ", " second " and " third " be may be used interchangeably by a component and separately
One component distinguishes, and is not intended to the position for indicating all parts or importance.
Term " preceding " and " rear " refer to the relative position in gas-turbine unit or propulsion device, and refer to combustion gas whirlpool
The normal operational attitude of turbine or propulsion device.For example, about gas-turbine unit, it is preceding to refer to closer to engine
The position of entrance then refers to the position closer to engine nozzle or exhaust.
Term " upstream " and " downstream " refer to the relative direction relative to the fluid flowing in fluid path.For example, " on
Trip " refers to fluid from the direction that it is flowed, and " downstream " refers to the direction that fluid is flowed to it.
Term " connection ", " fixation ", " attachment " etc. refer to directly coupling, fixed or attachment, and by one or
The indirect connection of multiple intermediate members or feature, fixed or attachment, except otherwise herein provided.
Unless the context clearly determines otherwise, otherwise singular " one ", "an" and "the" include plural.
The approximating language used in entire disclosure and claims is for modifying quantifying for any permissible variation
It indicates, the variation without will lead to relative basic function.Therefore, by one or more terms (such as " about ", " about "
" basic ") modification value be not limited to specified exact value.In at least some cases, approximating language can correspond to for surveying
The precision of the instrument of magnitude, or the precision of method or machine for constructing or manufacturing component and/or system.For example, approximate
Language also refers in the range of 10%.
Here and throughout the specification and claims, scope limitation is combined and exchanges, these ranges are identified simultaneously
Including all subranges wherein included, unless context or language are otherwise noted.For example, all ranges disclosed herein includes
Endpoint, and endpoint can combine independently of one another.
Referring now to the drawings, wherein identical number indicates that identical element, Fig. 1 are according to the disclosure throughout the drawings
Exemplary embodiment gas-turbine unit schematic cross-sectional view.More specifically, for the embodiment of Fig. 1, combustion
Gas eddy turbine is high bypassed turbine fan jet engine 10, hereon referred to as " turbofan 10 ".Such as Fig. 1 institute
Show, turbofan 10 limits axial direction A (be parallel to provide and extend for the longitudinal axis 12 of reference) and radial direction side
To R.Turbofan 10 also defines the circumferential direction C around axial direction A circumferentially extending (referring to Fig. 3).In general, whirlpool
Wheel fan 10 includes fan section 14 and the turbine 16 that 14 downstream of fan section is arranged in.
Shown in exemplary turbine 16 be generally enclosed in substantially tubular shape shell 18, shell 18 limit annular entry
20 and ring row port 21.Shell 18 with serial flow relationship encirclement: compressor section, the compressor section include booster or
Low pressure (LP) compressor 22 and high pressure (HP) compressor 24；Burning block 26；Turbine comprising 28 He of high pressure (HP) turbine
Low pressure (LP) turbine 30；With jet exhaust nozzle segment 32.HP turbine 28 is drivingly connected to by high pressure (HP) axis or spool 34
HP compressor 24.LP turbine 30 is drivingly connected to LP compressor 22 by low pressure (LP) axis or spool 36.Compressor section, burning
Section 26, turbine and nozzle segment 32 together define the core inlet air flow path 37 passed through.
The embodiment for shown in, fan section 14 include having the fixed knot of multiple fan blade 40 away from fan 38.Wind
Fan leaf 40 is each attached to disk 42, and fan blade 40 and disk 42 can be rotated together by LP axis 36 around longitudinal axis 12.For
Discribed embodiment, turbofan 10 is to directly drive turbofan, so that LP axis 36 directly drives wind
The fan 38 of sector field 14, without the use of reduction gear box.However, in other exemplary embodiments of the disclosure, fan 38
It can be alternatively variable pitch fan, and turbofan 10 may include reduction gear box, in this case,
LP axis 36 can cross over the fan 38 of gear-box driving fan section 14.
Referring still to the exemplary embodiment of Fig. 1, disk 42 is covered by rotatable front hub 48, and the front hub 48 is in air force
The air-flow promoted through multiple fan blade 40 is molded on.In addition, exemplary turbine Duct-Burning Turbofan 10 includes annular compartment
Body component 50, circumferentially about at least part of fan 38 and/or turbine 16.For discribed embodiment, cabin
Component 50 is supported by multiple circumferentially spaced export orientation airfoils 52 relative to turbine 16.In addition, cabin group
The downstream section 54 of part 50 extends on the outer portion of shell 18, to define therebetween bypass gas flow channel 56.By bypassing gas
First part's air of circulation road 56 and the entrance 20 by turbine 16 and second by core inlet air flow path 37
Dividing the ratio between air is commonly referred to as by-pass ratio.
It will be appreciated, however, that the exemplary turbine Duct-Burning Turbofan 10 described in Fig. 1 is only as an example, and at other
In exemplary embodiment, turbofan 10 can have any other suitable construction, including for example, any other is closed
The axis or spool of suitable quantity, turbine, compressor etc..Additionally or alternatively, in other exemplary embodiments, it can provide any
Other suitable turbogenerators.For example, in other exemplary embodiments, turbogenerator can not be turbofan and start
Machine, but can be structured as turboaxle motor, turboprop, turbojet etc..
Referring now to Figure 2, the myopia for providing the rear end of the turbine 16 of the exemplary turbine Duct-Burning Turbofan 10 of Fig. 1 is shown
It is intended to.Specifically, the myopia that Fig. 2 provides the LP turbine 30 of the turbine of the exemplary turbine Duct-Burning Turbofan 10 of Fig. 1 is shown
It is intended to.
As shown, LP turbine 30 generally includes the alternate level of airfoil, more specifically, including LP turbine rotor blade 60
The alternate level of (that is, rotating airfoils part) and LP turbine stator airfoil 62 (that is, fixed airfoil).It will thus be appreciated that such as this
Used in text, term " airfoil " is used to refer to rotor blade or guidance airfoil.In multiple LP turbine rotor blades 60
Each corresponding LP turbine rotor 66 is attached at base portion 64.The LP turbine rotor of every grade of LP turbine rotor blade 60
66, which are connected to adjacent LP turbine rotor 66-multiple LP turbine rotor 66, is also connected to LP axis 36 by LP shaft extension 68.Cause
This rotates multiple LP turbine rotor blades 60 and LP turbine rotor 66 by the flowing of the burning gases of LP turbine 30, this is again
Rotate LP axis 36.In addition, as noted, LP turbine 30 includes multistage LP turbine stator airfoil 62, every grade of LP turbine is fixed
Sub- airfoil 62 is attached to the shell 18 of turbine 16.As it will be appreciated, LP can be improved in the grade of LP turbine stator airfoil 62
The efficiency of turbine 30.For discribed embodiment, each grade of LP turbine stator airfoil 62 is located in LP turbine rotor leaf
Between the adjacent level of piece 60 or it is positioned adjacent to the level-one of LP turbine rotor blade 60.
In short, it should also be understood that LP axis 36 is supported by fore bearing 70 and rear bearing 72 for illustrated embodiment.However, answering
It should be appreciated that in other exemplary embodiments, LP axis 36 can be supported alternatively in any other suitable manner.Example
Such as, in other exemplary embodiments, fore bearing 70 and rear bearing 72 can be positioned at the front of the extended element 68 of LP axis 36,
Or optionally, the two may be positioned at the rear of the extended element 68 of LP axis 36.In addition, it should be understood that shown in although
Exemplary L P turbine 30 includes three-level LP turbine rotor blade 30 and LP turbine stator airfoil 62, but in other exemplary implementations
In example, LP turbine 30 may include the LP turbine rotor blade 60 and/or stator airfoil of any other suitable quantity and/or construction
62 grade.Including other constructions are also considered.
Referring still to Fig. 2, it should be understood that every in the LP turbine rotor blade 60 of the corresponding stage of LP turbine rotor blade 60
One extends between radial inner end 74 (radial inner end 74 for being connected to respective rotor 66) and radial outer end 76.In addition, shown
The turbine of exemplary turbine engine 10 include outer lining 78, grade and at least partly of the outer lining 78 around rotor blade 60
Ground limits the core inlet air flow path for passing through turbine (more specifically, LP turbine 30 shown in passing through).
It reference will also be made to Fig. 3 now, the most rear class of the LP turbine 30 of Fig. 2 according to the exemplary embodiment of the disclosure be provided
The schematic axial view of LP turbine rotor blade 60 has the abradable layered deposition system 100 therewith positioned (herein
In be known as " depositing system 100 "；It is described below).In the case where given functions described herein, depositing system 100 may be used also
To be referred to as " repair outfit ".
As shown, surrounding each grade of LP turbine rotor blade 60, outer lining 78 includes tyre 80.As used herein, art
Language " tyre " typically refers to any inner surface/component of the annulation around airfoil rotation grade.For example, may include in addition one
Or multiple shirt portion parts, shield sections etc..With particular reference to Fig. 3, around LP turbine rotor blade 60 specific grade (such as in Fig. 3 most
Rear class) tyre 80 further include the abradable layer 82 fixed to permanent base 84.Abradable layer 82 is configured to more with corresponding stage
76 close contact of radial outer end of a LP turbine rotor blade 60, to improve the efficiency of LP turbine 30.In addition, it should be understood that LP
Turbine 30, or more precisely, each of LP turbine rotor blade 60 grade limits gap 86,80 abradable layer 82 encloses in addition
Around the grade of such LP turbine rotor blade 60.In the entire ongoing operation of engine, in abradable layer 82 and LP turbine 30
To deciding grade and level LP turbine rotor blade 60 radial outer end 76 between gap 86 can increase.This may be due to for example existing
The expansion and contraction of various engine components during the normal operation cycle of engine.Anyway, the increasing of the size in gap 86
The efficiency that may cause turbogenerator 10 is added to reduce.
With particular reference to Fig. 3, depositing system 100 is provided to repair abradable layer 82 in situ to reduce the size in gap 86, and
Engine need not for example engine be removed and/or dismantled from the wing with the abradable layer of exposure.For discribed embodiment, sink
Product system 100 generally includes sensing module 102, jet module 104 and forming module (contour module) 106, for institute
The embodiment of description, each of these modules are operably linked to the controller 108 of depositing system 100.As schematically
Shown, controller generally includes one or more processors 109 and memory 111.Memory 111 can store data 113.Number
According to may include when by one or more processors 109 execute when make depositing system 100 execute function instruction.It for example closes below
Certain functions in these functions are described in the illustrative methods 300 of Figure 11.It is worth noting that, controller 108 passes through communication
Bus, more specifically, bus is operably linked to module 102, each of 104,106 (in such as Fig. 3 by wireless communication
Dotted line shown in).
In addition, as also shown, the embodiment for shown in, sensing module 102 is connected to the first LP turbine rotor blade
60A, jet module 104 is connected to the 2nd LP turbine rotor blade 60B, and forming module 106 is connected to the 3rd LP turbine and turns
Blades 60C.Turn more specifically, these modules 102, each of 104,106 are removably coupled to corresponding LP turbine
Blades 60A, 60B, 60C, so that they can be removed after completing repairing as described herein.It will be appreciated, however, that at it
In his embodiment, module 102,104, one or more of 106 can be installed to identical LP turbine rotor blade 60, or
(not being with sequence as shown in the figure) is spaced apart with any suitable rotor blade 60.
In addition, as from it will be understood that in following discussion, during the operation of depositing system 100, LP turbine rotor blade
60 grade (including the first LP turbine rotor blade 60A, the 2nd LP turbine rotor blade 60B and the 3rd LP turbine rotor blade
It can 60C) be rotated on circumferential direction C, more specifically, rotated on the first circumferential direction C1, so that modules 102,
104,106 can also move on the first circumferential direction C1 during the operation of depositing system 100.
Referring still to Fig. 3, now referring also to Fig. 4, sensing module 102 will be discussed.Fig. 4 provides the first LP turbine rotor leaf
Piece 60A on the pressure side 88 schematic close up view, wherein sensing module 102 is removably attached to thereon.For discribed reality
Example is applied, sensing module 102 includes the biography oriented towards the abradable layer 82 of the tyre 80 of the grade around LP turbine rotor blade 60
Sensor 110.Sensor 110 can be such as proximity sensor, so that sensing module 102 is determined in multiple LP turbines
The outer end 76 of rotor blade 60 and in addition between 80 along the measurement (usually using number " 90 ") in the gap 86 of radial direction R,
More specifically, in the outer end 76 of multiple LP turbine rotor blades 60 and in addition between 80 abradable layer 82 along radial direction R
Gap 86 measurement 90.
In addition, it will be appreciated that when depositing system 100 revolves during the operation of depositing system 100 along the first circumferential direction C1
When turning, in the radial direction R and along circumferential direction the two of the gap 86 of C can be determined using the depositing system 100 of sensing module 102
Dimension amount 90.More specifically, providing Figure 25 0 referring now briefly to Fig. 5, which depict the radial directions in multiple guidance airfoils
Outer end 76 and in addition between 80 in the radial direction R and along circumferential direction the measurement 90 in the gap 86 of C (more specifically, the first measurement
90A, as follows will be described).Specifically, Figure 25 0 depicts the measurement 90 in the gap 86 along the radial direction R along Y-axis 252
The circumferential position of value and the measurement 90 along the gap of X-axis 254 86 (as unit of degree, 0 degree and 360 degree is same position).Therefore,
It determines in any given circumferential position it should be appreciated that sensing module 102 can be used in depositing system 100 along radial side
To the measurement 90 in the gap of R 86, for discribed embodiment, which exists for any given position of C along circumferential direction
Change between about X and X'.In this way, C is non-uniform along circumferential direction in gap 86.
It referring back to Fig. 4, is such as also shown in, the illustrative sensors 110 of discribed sensing module 102 can be for given
Circumferential position generally axially direction A carries out multiple measurements (that is, determine multiple measurement 90).Example shown in for example, is sexy
The sensor 110 of survey module 102 may be able to determine that the axial midpoint close to LP turbine rotor blade 60, multiple LP turbine turns
The first measurement 90A in the gap 86 between the outer end 76 of blades 60 and in addition 80 abradable layer 82, close to LP turbine rotor
Gap 86 between the outer end 76 of the leading edge 92 of blade 60, multiple LP turbine rotor blade 60 and in addition 80 abradable layer 82
The second measurement 90B, and close to LP turbine rotor blade 60 rear 94, the outer ends 76 of multiple LP turbine rotor blades 60
The third in the gap 86 between 80 abradable layer 82 in addition measures 90C.
It is worth noting that, depicting in Fig. 5 in the radial direction R and along circumferential direction, the first of the gap 86 of C is measured
90.Also provide Figure 25 6 referring briefly to Fig. 6 and 7, Fig. 6 now, which depict it is multiple guidance airfoils radial outer ends 76 with
In addition along radial direction R and the second measurement 90B in the gap 86 of C along the circumferential direction between 80；And Fig. 7 provides figure
258, which depict the radial outer ends 76 of multiple guidance airfoils and in addition in the radial direction R and along circumferential direction C between 80
The third in gap 86 measures 90C.Specifically, Figure 25 6 depicts second degree of the gap 86 along the radial direction R along Y-axis 252
Measure 90B value and along X-axis 254 gap 86 second measurement 90B circumferential position (by degree as unit of, 0 degree and 360 degree is
Identical position)；And similarly, Figure 25 8 depicts the third measurement along the gap 86 of the radial direction R along Y-axis 252
The value of 90C and along X-axis 254 gap 86 third measurement 90C circumferential position (by degree as unit of, 0 degree and 360 degree is phase
Same position).It will thus be appreciated that depositing system 100 can also use sensing module 102 to determine in any given circumferential direction
The second measurement 90B in the gap 86 along radial direction R at position, and determine on the edge of any given circumferential position
The third in the gap 86 of radial direction R measures 90C, and for discribed embodiment, the second measurement 90B is for C along circumferential direction
Any given position change between about Y and Y', for illustrated embodiment, third measures 90C for C's along circumferential direction
Any given position changes between about Z and Z'.
Although it is worth noting that, describing three at the different location of in axial direction A for discribed embodiment
A individual measurement, but in other embodiments, it can be by the sensor 110 of sensing module 102 in axial direction A's
Any other appropriate number of measurement 90 is taken at different location.For example, in other embodiments, the sensing of sensing module 102
Device 110 can in axial direction A be spaced apart two positions at, in axial direction A be spaced apart four or more
Place is set, A is spaced apart up in ten or more the positions that in axial direction A is spaced apart, such as in axial direction
At 5000 positions, the measurement 90 of sensing gap 86.In this way, it should be understood that utilize the sensor of sensing module 102
110, depositing system 100 can determine gap 86 in the radial direction R, the three-dimensional measurement 90 of circumferential direction C and axial direction A.
Referring now to Fig. 8, provide the 2nd LP turbine rotor blade 60B on the pressure side 88 schematic close up view, wherein spraying
Module 104 is penetrated to be removably attached to thereon.The embodiment for shown in, jet module 104 generally include base portion 112 and distribution
First 114, wherein one or more dispenser nozzles 116 are positioned on and orient towards in addition 80, are used for abradable material
It deposits on tyre 80.More specifically, one or more dispenser nozzles 116 are configured to outside for abradable material to be assigned to
On abradable layer 82 with 80.
It should be appreciated that can be any suitable abradable material by the abradable material that jet module 104 deposits.Example
Such as, abradable material can be the abradable material based on rubber.In this case, base portion 112 and/or spray head 114 can wrap
Heater is included, to heat abradable material, to allow nozzle 116 to distribute abradable material in a manner of discribed.However, at it
In his exemplary embodiment, abradable material can be any other suitable material.In addition, it should be understood that it is as used herein,
Term " abradable " typically refers to be designed to lost material when with another material friction.Specifically, used herein
In context, abradable material, which refers to, is designed to lost material when the outer end of rotating airfoils part 76 rubs with it.
Referring still to the embodiment of Fig. 8, one or more dispenser nozzles 116 in multiple dispenser nozzles 116 are substantially
In axial direction A is separated from each other.More specifically, for discribed embodiment, one or more dispenser nozzles 116 include
Two dispenser nozzles 116 that A is separated from each other generally in the axial direction.However, in other embodiments, one or more point
Orchestration nozzle 116 may include any other appropriate number of dispenser nozzle 116, such as single dispenser nozzle 116, three or
More dispenser nozzles 116, five or more dispenser nozzles 116, or up to such as about 20 distributor sprays
Mouth 116.
In some of the exemplary embodiments, base portion 112 may include the abradable material of certain volume, will be by one or more
A dispenser nozzle 116 deposits.However, in other embodiments, one or more dispenser nozzles 116 can pass through fluid hose
118 are fluidly coupled to the source that the base portion 112 far from jet module 104 positions, such as in the shown embodiment.For example, fluid hose
118 by hole in turbogenerator 10 (for example, borescope hole, fuel nozzle opening, igniter opening etc.) or can pass through
The core inlet air flow path 37 of turbogenerator 10 is supplied to pedestal 112.
As noted, one or more dispenser nozzles 116 are configured to for abradable material to be deposited to tyre 80
Abradable layer 82 on.In some of the exemplary embodiments, it can control jet module 104 to provide with C along the circumferential direction
The abradable material of even amount, or can control jet module 104 and provide uneven amounts of abradable material with C along the circumferential direction
Material.For example, jet module 104 can be configured to provide in certain circumferential positions using one or more dispenser nozzles 116
The abradable material of incrementss, in the circumferential position, gap 86 is measured as being more than or less than other regions.In this way,
Depositing system 100 can be capable of providing new abradable material layer, so that obtained abradable layer 82 turns in multiple LP turbines
The radial outer ends 76 of blades 60 and the desired gap 86 for limiting C along circumferential direction between 80 in addition, although lower layer/rise begins
Wearing course 82 is uneven.For example, in the radial direction R and along circumferential direction C depicts the abradable layer of gained referring briefly to Fig. 5
The measurement 260 in the gap 86 between the outer end 76 of 82 and LP turbine rotor blade 60.As shown, the embodiment for shown in,
Measurement 260 is the substantially homogeneous radial values X " of C along circumferential direction.
Referring still to Fig. 8, it should be understood that exemplary jet module 104 can also change in axial direction A and provide in addition
The amount of abradable material on 80 existing/following abradable layer 82.In this way, jet module 104 by one or
Multiple dispenser nozzles 116 can also provide the abradable material of in axial direction A uneven gauge.
For example, depositing system 100 can the leading edge 92 of LP turbine rotor blade 60 be provided about one layer it is new abradable
Material is different from the amount that axial midpoint is provided about and different from the amount near rear 94.For example, referring again to figure
6 and Fig. 7, Fig. 6 show the abradable layer 82 of gained and LP turbine of the in the radial direction R and along circumferential direction close leading edge 92 of C
Second measurement 262 in the gap 86 between the outer end 76 of rotor blade 60, C has substantially homogeneous radial values along circumferential direction
Y"；Fig. 7 shows the abradable layer 82 of gained and LP turbine rotor of the in the radial direction R and along circumferential direction close rear 94 of C
The third measurement 264 in the gap 86 between the outer end 76 of blade 60, C has substantially homogeneous radial values Z " along circumferential direction.
In addition, still referring generally to Fig. 5 to Fig. 7, for given circumferential position, such as 90 degree of circumferential positions, injection
Module 104 can deposit (the figure of first thickness 266 of abradable material near the axial midpoint of LP turbine rotor blade 60
5) second thickness 268 (Fig. 6) of abradable material, is deposited near the leading edge 92 of LP turbine rotor blade 60, and in LP turbine
The rear 94 of rotor blade 60 nearby deposits the third thickness 270 (Fig. 7) of abradable material.In this way, obtained can
Wearing course 82 can have different thickness in any given circumferential position and axial positions, and/or any given
Circumferential position and axial positions can have identical thickness, although the pattern of lower layer is different.As an example, Fig. 5 is with dotted line
Show line 261, line 261 indicates the in the radial direction R and along circumferential direction potential measurement in the gained gap 86 of C, wherein gained
The measurement 90A in gap 86 C variation/uneven along circumferential direction.
Referring now to Fig. 9, provide the 3rd LP turbine rotor blade 60C on the pressure side 88 schematic close up view, wherein at
Pattern block 106 is removably attached to thereon.The embodiment for shown in, forming module 106 generally include base portion 120 and molding
Component (contour member) 122, shaped component 122 pass through one or more adjutages 124 and are attached to base portion 120.For
Discribed embodiment, shaped component 122 are generally constructed with the blade of contoured edge (contouring edge) 126, at
Type edge 126 is configured in the abradable material deposited recently in addition 80 " scraping ".In this way, shaped component 122
It is desired to may insure that obtained abradable layer 82 limits, the surface of relative smooth and/or desired thickness.It should be appreciated that
Although the contoured edge 126 of shaped component 122 be for the embodiment of Fig. 9 it is substantial linear, in other exemplary realities
It applies in example, the contoured edge 126 of shaped component 122 can have any other suitable shape.
In addition, as described above, shaped component 122, which passes through one or more adjutages 124, is attached to base portion 120.More specifically
Ground, the embodiment for shown in, shaped component 122 are attached to base portion by the first adjutage 124A and the second adjutage 124B
A is separated from each other generally in the axial direction by 120, the first adjutage 124A and the second adjutage 124B.First and second adjutages
124A, 124B can be moved in the radial direction R, to change the gained radial position of the contoured edge 126 of shaped component 122.With
This mode, shaped component 122 can be used for changing multiple LP turbines by the positioning of the first and second adjutage 124A, 124B and turn
The result measurement 90 in the gap 86 between the outer end 76 and tyre 80 of blades 60.
It is worth noting that, in certain embodiments, the first adjutage 124A (can be shown along radial direction R with dotted line
Moving direction out) it is mobile relative to the second adjutage 124B, so that forming module (contour module) 106 can be used for
For any given circumferential position change the in axial direction gap 86 of A result measurement (for example, size 90A, 90B,
90C).It should be appreciated that jet module 104 can be not configured to change in axial direction A and spray in such exemplary embodiment
The amount for the abradable material penetrated, and alternatively depositing system 100 can use shaped component 122 to provide in axial direction A
Gap 86 result measurement 90 variation.However, in other exemplary embodiments, single adjutage 124 can be used for by
Type component 122 is connected to base portion 120, or optionally, and shaped component 122 can be connected to base portion 120 in a position-stable manner, or
Optionally, any other appropriate number of adjutage 124 can be by multiple shaped components 122 (for example, axially arranging) connection
To base portion 120.
In addition, it should be understood that at least some of exemplary embodiment, in addition to keeping the abradable material deposited recently smooth
Except, shaped component 122 can also be used as scraper, removed before depositing abradable material using jet module 104 existing
There is at least part of abradable layer 82.For such construction, identical shaped component 122 can be used, or replaceable
Ground, shaped component 122 can be switched for such operation.In addition, alternatively, other systems or structure can be used
It makes to prepare abradable layer 82 to receive new abradable material.
It will be appreciated, however, that in other exemplary embodiments, it is suitable that depositing system 100 can have any other
Construction.For example, Exemplary Deposition System 100 may include reshaping module in other exemplary embodiments of the disclosure
Any other construction of (recontouring module) 106, or it is alternatively possible to do not include reshaping module 106.This
Outside, in other illustrative aspects, sensor module 102 may include any other appropriate number of sensor 110, various modules
102,104,106 can be removably attached to the airfoil etc. that C along the circumferential direction is spaced farther apart from.
In addition, it will be appreciated that in other exemplary embodiments, any other suitable depositing system 100 can be used
By abradable material in situ be applied to around rotation grade airfoil tyre 80 (i.e., it is not necessary to engine is removed from the wing and/
Or disassembly engine is to expose the part repaired).For example, providing referring now to Figure 10 according to another example of the disclosure
Property embodiment depositing system 100, for executing this in situ repair.Figure 10 is provided according to an exemplary embodiment of the present disclosure
Turbofan 10 turbine 16 rear end schematic close up view.More specifically, Figure 10 provides exemplary turbine
The schematic close up view of the LP turbine 30 of the turbine of Duct-Burning Turbofan 10.It should be appreciated that at least some of exemplary embodiment
In, the LP turbine 30 described in Figure 10 can with 30 substantially similar way of exemplary L P turbine that is described above with reference to Fig. 2
Construction.Therefore, the same or similar part of the same or similar digital representation.
For example, as shown, LP turbine 30 generally includes multistage LP turbine rotor blade 60, with multistage LP turbine stator
Airfoil 62 is alternately spaced apart.Each of LP turbine rotor blade 60 of the corresponding stage of LP turbine rotor blade 60 is even
It is connected between the radial inner end 74 of respective rotor 66 and radial outer end 76 and extends.In addition, discribed turbine includes outer lining
78, outer lining 78 at least partially defines the core inlet air flow path 37 across turbine, and more specifically, passes through shown
LP turbine 30.More specifically, surrounding each grade of LP turbine rotor blade 60, outer lining 78 includes tyre 80, and 80 have in addition
Abradable layer 82 fixed to permanent base 84 (see, for example, Fig. 3).It should be appreciated that LP turbine 30, or more precisely, LP
Each of turbine rotor blade 60 grade limits gap 86, and 80 abradable layer 82 surrounds such LP turbine rotor blade 60 in addition
Grade.
In addition, providing depositing system 100 according to the another exemplary embodiment of the disclosure.Exemplary Deposition System 100
It is configured to for abradable material to be ejected into the abradable of a part of the tyre 80 of the LP turbine rotor blade 60 around specific grade
Layer 82.More specifically, depositing system 100 is configured to snakelike arm tool for discribed embodiment, it is configured to extend through
Cross the opening of turbogenerator 10.For discribed embodiment, snakelike arm tool generally includes snakelike arm 130 and base portion 132,
Wherein snakelike arm 130 is connected to base portion 132.Snakelike arm 130 includes positioned at the practical head 134 of its distal end, for shown implementation
Example, the practical head 134 include that the spraycan being coupled (sprays for example, being used to spray the one or more of abradable material
Mouth).In addition, the base portion 132 of snakelike arm tool includes one or more motors 136 and controller 138, one or more motors
136 can operate together with snakelike arm 130, so that snakelike arm 130 is moved to desired position/orientation along desired direction.Control
Device 138 is also operably linked to one or more motors 136, for operating one or more motors 136, and then operates snakelike
Arm 130.
For discribed embodiment, the exhaust section 32 that snakelike arm 130 extends through turbogenerator 10 reaches the whirlpool LP
The grade of rotor blades 60 allows it that abradable material is ejected into grade around such LP turbine rotor blade 60
On abradable layer 82.It will be appreciated that though the practical head 134 of snakelike arm tool is solid with nozzle 116 for the embodiment of Figure 10
It is fixed, but in other embodiments, the practical head 134 of snakelike arm tool can be additionally or alternatively fixed with: sensor, be used
The measurement in the gap 86 between the outer end 76 and tyre 80 for determining multiple LP turbine rotor blades 60；Shaping jig
(contouring tool), for carrying out reshaping to the abradable material deposited in addition 80 for example, by nozzle 116
(re-contouring)；Scraper, it is existing for removing at least part before being ejected into new abradable material on tyre 80
There is material；Or any other suitable or desired tool.
It is worth noting that, in other exemplary embodiments, should be managed although being discussed with reference to LP turbine 30
Solution, depositing system 100 can be used together with the other component of turbogenerator 10.For example, turbogenerator 10 may include tool
There are various other components of one or more airfoil rotations grade (for example, rotor blade rotation grade), is enclosed wherein tyre 80 has
Around the abradable layer 82 of this rotation grade airfoil.For example, HP compressor 24, one in LP compressor 22 and HP turbine 28 or
Multiple may include the grade of the rotating airfoils part surrounded by the tyre 80 with abradable layer 82.In addition, in certain embodiments, tool
The fan 38 for having fan blade 40 may include the tyre (in outer cabin 50/in) with abradable layer 82.In some embodiments
In, depositing system 100 can be used together with any such component.
Referring now to Figure 11, providing the method for repairing turbogenerator of the illustrative aspect according to the disclosure
300.In at least some of illustrative aspect, method 300 can be with the turbogenerator discussed above with reference to such as Fig. 1 to 10 and heavy
Product system is used together.It will thus be appreciated that turbogenerator generally includes airfoil rotation grade and rotates grade around airfoil
Tyre.Airfoil rotation grade includes multiple airfoils, and airfoil limits the outer end of the radial direction along turbogenerator.
The measurement that method 300 is typically included in the gap between the outer end and tyre for determining multiple airfoils at (302) is big
In predetermined amount.In at least some of illustrative aspect, determine that the measurement in gap may include between determining using sensor at (302)
The measurement of gap.
In addition, determining that the measurement in gap can include determining that the list in gap at (302) at least some of illustrative aspect
Point measurement (for example, along the width in the gap at the single location of the circumferential direction of engine radially).However, at it
The illustrative aspect described in his illustrative aspect, such as Figure 11 determines that the measurement in gap further includes in (304) at (302)
Place determines the radial direction along turbogenerator and the two dimension measurement in gap along circumferential direction.For example, method 300 can be
(304) determined at given axial positions and multiple circumferential positions (for example, at least about eight circumferential positions, for example, at least about 12
A circumferential position, for example, at least about 20 circumferential positions, such as up to about 10,000 circumferential position) at gap degree
Amount.In this way, sensor (or multiple sensors) can be a part of sensing module, and sensing module can be coupled
To one or more airfoils of airfoil rotation grade.Airfoil rotation grade and sensing module can determine gap at (302)
Measurement during rotate, to determine the radial direction along turbogenerator and the two dimension measurement in gap along circumferential direction.
Referring still to Figure 11, it should be understood that at least some of illustrative aspect, in addition to determining gap at (304) two
Except dimension amount, determines that the measurement in gap can further include at (302) and determined at (306) in axial direction, diameter
To the three-dimensional measurement in direction and the gap of circumferential direction.Using such illustrative aspect, in addition to the two dimension determined at (304)
Except measurement, method 300 can also determine this two dimension measurement, for example, at least about two axial positions in various axial positions
It sets, for example, at least about three axial positions, for example, at least about five axial positions, such as up to about 5000 axial positions.
In addition, method 300 may further include in the certain illustrative aspects for the method 300 described in Figure 11
(308) at least part in situ for removing existing abradable material at.For example, in situ remove at least partially can at (308)
Wear material may include wiping a part of abradable material off.For example, in situ at (308) remove at least part abradable material
It may include at least part for removing existing abradable material before (309A) is in the measurement for determining gap at (302), make
It obtains before determining the measurement in gap, removes any loose abradable material first.Alternatively, in situ at (308) remove extremely
Few a part of abradable material may include removing at least part now after (309B) is in the measurement for determining gap at (302)
There is abradable material, so that removing the desired amount of abradable material to generate required gap.It should be noted, however, that at it
His illustrative aspect, method 300 can not include such removing step.
It is in addition, method 300 is additionally included in (310) and outer takes in-situ deposition abradable material to reduce multiple aerofoil profiles
The measurement in the gap between the outer end and tyre of part.For discribed illustrative aspect, the outer original position that takes is in (310) and is sunk
Product abradable material includes using at least one airfoil being attached in multiple airfoils at (312) (for example, removedly
Attachment) jet module deposit abradable material.In addition, taking original outside (310) are in using such illustrative aspect
Position deposition abradable material further includes rotating multiple airfoils at (314), while taking deposition abradable material outside.
In certain illustrative aspects, being in the outer deposition abradable material that takes in (310) may include taking spraying outside
The layer of substantially homogeneous abradable material.However, taking original position outside (310) are in for illustrative aspect shown in Figure 11
Deposition abradable material is included in (316) and is in outer take deposits abradable material in an uneven manner along circumferential direction.Example
Such as, using such illustrative aspect, method 300 can use the two dimension measurement in the gap determined at (302) to determine
(316) heterogeneous fashion of abradable material is deposited at.For example, method 300 is using two of gap determined by (302)
Dimension amount deposits abradable material at (316) in an uneven manner so that along circumferential direction with the gap of radial direction
Result measurement it is substantially consistent.Additionally or alternatively, such as in the illustrative aspect shown in, unevenness is sentenced in (316)
Even mode deposit abradable material be included at (318) along the circumferential direction in an uneven manner deposition abradable material with
Lead to the non-uniform two dimension measurement radially with the gap of circumferential direction.Additionally or alternatively, such as shown in
In illustrative aspect, deposited in an uneven manner at (316) abradable material be included at (318) along the circumferential direction with
Non-uniform mode deposits abradable material to lead to the radially uneven two dimension measurement with the gap of circumferential direction.It is logical
Cross such illustrative aspect, can determine each circumferential position (for example, it is known more or more than other circumferential positions
The circumferential position of expansion or shrinkage less) it include additional abradable material with the efficiency for improving turbogenerator will be beneficial
's.
It is worth noting that, although being discussed with reference to the jet module for being attached at least one of multiple rotating airfoils parts
Abradable material is deposited at (310) above, but in other illustrative aspects, any other suitable deposition system can be used
System.For example, shown in dotted line, in other certain illustrative aspects, depositing abradable material at (310) may include in (319)
Place uses the snakelike arm tool in-situ deposition abradable material for extending through the opening of turbogenerator.
In addition, in certain illustrative aspects, method 300 can be utilized further to be determined at (306) although being not shown
Gap three-dimensional measurement.For example, depositing abradable material at (310) may include the gap for considering to determine at (306)
Three-dimensional measurement to deposit abradable material, to generate the three-dimensional measurement in desired gap.More specifically, being deposited at (310)
Abradable material may include in axial direction depositing abradable material in an uniform way, or optionally, in axial direction with not
Non-uniform manner deposits abradable material.The measurement that can permit obtained gap in this way limits desired 3D shape.
Also as shown in Figure 11, method 300 is included in original position reshaping (recontouring) at (320) and is deposited in addition
On abradable material.The illustrative aspect for shown in, original position reshaping abradable material is included in (322) at (320)
Place is in situ again using the reshaping tool (recontouring tool) at least one airfoil being attached in multiple airfoils
The abradable material that molding deposition takes outside.More specifically, the illustrative aspect for shown in, at (320) it is in situ again at
Type, which is deposited on the abradable material taken outside and is included at (324), rotates multiple airfoils, while reshaping in situ is deposited on
The abradable material taken outside.
It should be appreciated that using the depositing system of one or more illustrative aspects according to the disclosure, and/or execute basis
The repairing of the turbogenerator of one or more illustrative aspects of the disclosure, can permit engine and spends more between repairing
More times are on the wing.More specifically, being executed in situ by using one or more exemplary deposition tools for example as described herein
The repairing of abradable layer can fix over an engine in the case where not needing and engine being removed and/or dismantled from the wing.In this way
It can save a lot of time and cost.
This written description uses examples to disclose the present invention, including optimal mode, and also enables those skilled in the art
Enough practice present invention, the method including manufacturing and using any device or system and executing any combination.Of the invention can be special
Sharp range is defined by the claims, and may include other examples that those skilled in the art expect.If these other examples
Including the structural detail not different from the literal language of claim, or if they include the literal language with claim
Say the equivalent structural elements without essential difference, then these other examples are intended within the scope of the claims.
Various features of the invention, aspect and advantage can also be embodied in various technical solutions described in following item item
In, these schemes can combine in any combination:
1. a kind of method for repairing turbogenerator, which is characterized in that the turbogenerator includes airfoil rotation
Turn grade and the tyre around airfoil rotation grade, the airfoil rotation grade includes the multiple airfoils for limiting outer end, institute
The method of stating includes:
Determine that the measurement in the gap between the outer end of the multiple airfoil and the tyre is greater than predetermined amount；With
By abradable material in-situ deposition it is described it is outer take, with reduce the outer end of the multiple airfoil with it is described
The measurement in the gap between tyre.
2. according to method described in item item 1, which is characterized in that wherein by the abradable material in-situ deposition described outer
Taking including using the jet module at least one airfoil being attached in the multiple airfoil can grind described in depositing
Consumption material.
3. according to method described in item item 2, which is characterized in that wherein by the abradable material in-situ deposition described outer
Take further comprises rotating the multiple airfoil, while the abradable material in-situ deposition being taken outside described.
4. according to method described in item item 1, which is characterized in that wherein the turbogenerator limits radial direction and circumferential direction
Direction, and wherein determine the measurement packet in the gap between the outer end of the multiple airfoil and the tyre
Include the two dimension measurement determined along the gap of the radial direction and the circumferential direction.
5. according to method described in item item 1, which is characterized in that wherein the turbogenerator limits axial direction, radial direction
Direction and circumferential direction, and wherein determine the gap between the outer end of the multiple airfoil and the tyre
The measurement includes the three dimensionality determined along the gap of the axial direction, the radial direction and the circumferential direction
Amount.
6. according to method described in item item 1, which is characterized in that wherein the turbogenerator limits circumferential direction, and
Wherein by the abradable material in-situ deposition it is described it is outer take including by the abradable material along the circumferential direction with
Non-uniform mode is deposited on outside described and takes.
7. according to method described in item item 6, which is characterized in that by the abradable material along the circumferential direction with unevenness
Even mode is deposited including depositing the abradable material in an uneven manner along the circumferential direction, to cause along described
The uneven measurement in the gap of circumferential direction.
8. according to method described in item item 1, which is characterized in that further comprise:
It is in situ to remove the existing abradable material of at least part.
9. according to method described in item item 1, which is characterized in that further comprise:
Reshaping in situ is deposited on the outer abradable material taken.
10. according to method described in item item 9, which is characterized in that wherein reshaping in situ is deposited on the outer institute taken
It is in situ including the use of the reshaping tool at least one airfoil being attached in the multiple airfoil to state abradable material
Reshaping is deposited on the outer abradable material taken.
11. according to method described in item item 10, which is characterized in that wherein reshaping in situ is deposited on the outer institute taken
Stating abradable material further comprises rotating the multiple airfoil, while reshaping in situ is deposited on the outer institute taken
State abradable material.
12. according to method described in item item 1, which is characterized in that the wherein the multiple aerofoil profile of the airfoil rotation grade
Part is multiple rotor blades.
13. according to method described in item item 1, which is characterized in that wherein by the abradable material in-situ deposition described
It takes outside including using the snakelike arm tool for the opening for extending through the turbogenerator to carry out abradable material described in in-situ deposition
Material.
14. a kind of for repairing the mechanic for surrounding the abradable layer of the tyre of airfoil rotation grade of turbogenerator
Tool, which is characterized in that the repair outfit includes:
Sensing module, the sensing module include sensor, and the sensor is configured to sensing the first airfoil of instruction
The data of the measurement in the gap between the abradable layer of the tyre；With
Jet module, the jet module are configured on the airfoil for being removably attached to the airfoil rotation grade,
The jet module includes the nozzle for being ejected into abradable material on the abradable layer.
15. according to repair outfit described in item item 14, which is characterized in that wherein the jet module is configured to removable
Except ground is attached to the second airfoil of the airfoil rotation grade, and wherein the sensing module is configured to removedly
It is attached to the first airfoil of the airfoil rotation grade.
16. according to repair outfit described in item item 14, which is characterized in that further comprise:
Forming module, the forming module are configured to the abradable material that reshaping is ejected on the abradable layer
Material.
17. according to repair outfit described in item item 16, which is characterized in that wherein the forming module is configured to removable
Except ground is attached to the third airfoil of the airfoil rotation grade.
18. according to repair outfit described in item item 14, which is characterized in that further comprise:
Controller, wherein the sensing module and the jet module are operably linked to the controller.
19. according to repair outfit described in item item 18, which is characterized in that wherein the controller includes at one or more
Device and memory are managed, wherein the memory stores data, the data include working as to be executed by one or more of processors
When so that the repair outfit is executed the instruction of function, the function includes radial direction and the edge determined along the turbogenerator
The two dimension measurement in the gap of the circumferential direction of the turbogenerator.
20. according to repair outfit described in item item 19, which is characterized in that wherein the function further comprise determining along
The radial direction, along the circumferential direction and along the turbogenerator axial direction the gap three-dimensional
Measurement.
Claims (10)
1. a kind of method for repairing turbogenerator, which is characterized in that the turbogenerator includes airfoil rotation grade
With the tyre around airfoil rotation grade, the airfoil rotation grade includes the multiple airfoils for limiting outer end, the side
Method includes:
Determine that the measurement in the gap between the outer end of the multiple airfoil and the tyre is greater than predetermined amount；With
By abradable material in-situ deposition it is described it is outer take, with reduce the multiple airfoil the outer end and the tyre
Between the gap the measurement.
2. the method according to claim 1, wherein wherein by the abradable material in-situ deposition described outer
Taking including using the jet module at least one airfoil being attached in the multiple airfoil can grind described in depositing
Consumption material.
3. according to the method described in claim 2, it is characterized in that, wherein by the abradable material in-situ deposition described outer
Take further comprises rotating the multiple airfoil, while the abradable material in-situ deposition being taken outside described.
4. the method according to claim 1, wherein wherein the turbogenerator limits radial direction and circumferential direction
Direction, and wherein determine the measurement packet in the gap between the outer end of the multiple airfoil and the tyre
Include the two dimension measurement determined along the gap of the radial direction and the circumferential direction.
5. the method according to claim 1, wherein wherein the turbogenerator limits axial direction, radial direction
Direction and circumferential direction, and wherein determine the gap between the outer end of the multiple airfoil and the tyre
The measurement includes the three dimensionality determined along the gap of the axial direction, the radial direction and the circumferential direction
Amount.
6. the method according to claim 1, wherein wherein the turbogenerator limits circumferential direction, and
Wherein by the abradable material in-situ deposition it is described it is outer take including by the abradable material along the circumferential direction with
Non-uniform mode is deposited on outside described and takes.
7. according to the method described in claim 6, it is characterized in that, by the abradable material along the circumferential direction with unevenness
Even mode is deposited including depositing the abradable material in an uneven manner along the circumferential direction, to cause along described
The uneven measurement in the gap of circumferential direction.
8. the method according to claim 1, wherein further comprising:
It is in situ to remove the existing abradable material of at least part.
9. the method according to claim 1, wherein further comprising:
Reshaping in situ is deposited on the outer abradable material taken.
10. according to the method described in claim 9, it is characterized in that, wherein reshaping in situ is deposited on the outer institute taken
It is in situ including the use of the reshaping tool at least one airfoil being attached in the multiple airfoil to state abradable material
Reshaping is deposited on the outer abradable material taken.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US15/988,708 US10815783B2 (en) | 2018-05-24 | 2018-05-24 | In situ engine component repair |
| US15/988,708 | 2018-05-24 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110524186A true CN110524186A (en) | 2019-12-03 |
| CN110524186B CN110524186B (en) | 2022-05-13 |
Family
ID=66625064
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910436217.XA Active CN110524186B (en) | 2018-05-24 | 2019-05-23 | In situ engine component repair |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US10815783B2 (en) |
| EP (1) | EP3572626A1 (en) |
| CN (1) | CN110524186B (en) |
| CA (1) | CA3043724A1 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20210138604A1 (en) * | 2019-11-07 | 2021-05-13 | Pratt & Whitney Canada Corp. | Tool for shaping abradable liners of gas turbine engines |
| FR3117390B1 (en) * | 2020-12-11 | 2024-01-19 | Safran Aircraft Engines | TOOLS FOR MACHINING AN ABRADABLE ANNULAR LAYER OF A FAN CASING OF AN AIRCRAFT TURBOMACHINE AND METHOD FOR MACHINING USING SUCH TOOLS |
| US11433491B1 (en) * | 2021-07-14 | 2022-09-06 | Andritz Hydro Corp. | Resurfacing discharge ring of hydraulic turbine with runner in place |
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Also Published As
| Publication number | Publication date |
|---|---|
| US10815783B2 (en) | 2020-10-27 |
| CA3043724A1 (en) | 2019-11-24 |
| US20190360338A1 (en) | 2019-11-28 |
| CN110524186B (en) | 2022-05-13 |
| EP3572626A1 (en) | 2019-11-27 |
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